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Consider an air-standard gas Turbine cycle with a regenerator heat exchanger. The operating compression ratio oand a maximum combustion temperature of the system are 12 and 1200 C respectively. The state of the air at intake is given as pressure of 0.1 MPa and temperature of 20 C. The Assume efficiencies of turbine, compressor and regenerators as 90%. Determine the pressure and temperature at each point in the cycle and the thermal efficiency. Give a summary table for the ratings for each component of the gas turbine system.
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Determine the internal normal force, shear force, and moment at point C in the simply supported beam. Point C is located just to the right of the 1500 couple moment.
steam enters an adiabatic turbine steadily at 3 mpa and 400 degree c and leaves at 50 kpa and 100 degree c. if the
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